Miniature Joule–Thomson (JT) Cryocoolers for Propellant Management

2004 ◽  
Author(s):  
W. Notardonato ◽  
G. Haddad ◽  
K. V. Krishna-Murty ◽  
J. Zhu ◽  
J. S. Kapat ◽  
...  
Keyword(s):  
Space Vehicle ◽  
Thermodynamic Cycle ◽  
Space Mission ◽  
Rapid Cool ◽  
304 Stainless Steel ◽  
Liquid Oxygen ◽  
External Temperature ◽  
Transfer Line ◽  
Heat Recuperator ◽  
Cryogenic Propellants

Boil-off of cryogenic propellants is an issue of concern in any space mission. There could be boil-off of liquid propellants in the cryogenic storage tank, transfer line or in the space vehicle external tank itself due to heat leak. The current insulation technology uses a multilayered thermal protective coating of 304 Stainless Steel and Welded Invar, which allows the propellant to withstand the extreme internal and external temperature variations generated during pre-launch, launch, and flight operations, which does not provide for zero boil-off (ZBO). Usage of a cryocooler to prevent propellant boil-off would potentially reduce the launch costs. Owing to its attractive features like simplicity, compactness and rapid cool-down characteristics, an innovative concept of using Joule-Thomson (JT) cryocoolers for prechilling, densification and ZBO applications of cryogenic propellants is focused upon. The liquid oxygen propellant transfer line at NASA Kennedy Space Center is considered for demonstration of the above concept. Various thermodynamic cycle parameters are optimized for the cryocooler to make the demonstration possible. Cycle optimization is done also taking into account the feasibility to develop some crucial components for the JT cryocooler like a micro channel heat recuperator and cold heads. Current state of developments in the heat exchanger is briefly described. Some advantages of using miniaturized cryocoolers in launch vehicle operations are also discussed.

A Helium Face Seal Application In a Liquid Oxygen Pump

1969 ◽  
Vol 91 (4) ◽  
pp. 668-674
Author(s):  
Walter J. Cieslik
Keyword(s):  
Electric Motor ◽  
Space Vehicle ◽  
Vibration Damping ◽  
The Other ◽  
Liquid Oxygen ◽  
Development Effort ◽  
Face Seal ◽  
Shaft Seal ◽  
Oxygen Pump ◽  
Helium Gas

The object of the work discussed in this paper was to develop a reliable helium gas shaft seal for use in an electric motor-driven, liquid oxygen pump on a space vehicle. The development effort covered tests on two basically different face seal designs, one with an attached carbon face and the other with a floating lap-fitted carbon face. Several bellows vibration damping devices and various seal material combinations were investigated.

Fluid Mode Excitation in Launch Vehicle Feed Lines Induced by Pogo Accumulator Venting

2014 ◽  
Author(s):  
Kirk W. Dotson ◽  
Brian H. Sako ◽  
Trinh T. Nguyen
Keyword(s):  
Space Vehicle ◽  
Launch Vehicle ◽  
Liquid Oxygen ◽  
Rocket Engines ◽  
Launch Vehicles ◽  
Feed Line ◽  
Large Pressure ◽  
Structural Responses ◽  
Flow Oscillations ◽  
Liquid Rocket

Launch vehicles with liquid rocket engines have feed lines through which propellants flow to the engine. To prevent feedback between structural responses and propellant pressure and flow oscillations, a compliant device called a pogo accumulator is typically installed in the propellant feed line. Even if a catastrophic interaction is thus averted, the fluid-induced structural responses may exceed those for important flight events such as liftoff and atmospheric buffeting. In that case, the fluid-induced excitation must be predicted in order to ensure adequate structural margins for the launch vehicle and space vehicle hardware. Venting of compliant gas in the pogo accumulator prior to engine shutdown is known to exacerbate the fluid-induced excitation. In particular, for the Atlas V launch vehicle, a 5–7 Hz fluid mode with large pressure gains at the aft end of the liquid oxygen feed line often excites structural modes just prior to engine cutoff. A methodology for the prediction of these structural responses is presented.

scholarly journals Missions to Phobos and Other Minor Bodies

2002 ◽  
Vol 12 ◽  
pp. 642-645 ◽  
Author(s):  
Vsevolod S. Avduevsky ◽  
Efraim L. Akim ◽  
Timur M. Eneev ◽  
Mikhail Ya. Marov ◽  
Stanislav D. Kulikov ◽  
...  
Keyword(s):  
Space Vehicle ◽  
Space Mission ◽  
Vehicle Design ◽  
Sample Return ◽  
New Generation

AbstractA space mission to Mars’ moon Phobos with a space vehicle of new generation currently developed by the Russian Aerospace Agency is discussed. The vehicle design incorporates innovative SEP technology focused on small propulsion electric engines which significantly improve the mission energetic capability. The project is optimized around a sample return (PSR) from Phobos and also offers an opportunity for rendezvous/sample return missions from several asteroids, comets, and NEO. Scenario, rationale, and basic profile of PSR mission are presented.

Liquid Methane and Liquid Oxygen Horizontal Chilldown Experiments of a 2.54 and 11.43 Centimeter Transfer Line

2022 ◽  
pp. 118042
Author(s):  
Jason Hartwig ◽  
Peter Meyerhofer ◽  
Benjamin Stiegemeier ◽  
Robert Morehead
Keyword(s):  
Liquid Oxygen ◽  
Transfer Line ◽  
Liquid Methane

Comparison of Recovery and Recrystallization in Stainless Steel Following Plane-Wave Shock Loading and Explosive Forming

1970 ◽  
Vol 28 ◽  
pp. 428-429 ◽  
Author(s):  
J. A. Korbonski ◽  
L. E. Murr
Keyword(s):  
Stainless Steel ◽  
Shock Loading ◽  
Pressure Pulse ◽  
Shock Pressure ◽  
304 Stainless Steel ◽  
Strain Rates ◽  
Two Dimensional ◽  
Aisi 304 Stainless Steel ◽  
Aisi 304 ◽  
Explosive Forming

Comparison of recovery rates in materials deformed by a unidimensional and two dimensional strains at strain rates in excess of 104 sec.−1 was performed on AISI 304 Stainless Steel. A number of unidirectionally strained foil samples were deformed by shock waves at graduated pressure levels as described by Murr and Grace. The two dimensionally strained foil samples were obtained from radially expanded cylinders by a constant shock pressure pulse and graduated strain as described by Foitz, et al.

Pyrolytic carbon filaments and associated catalytic particles formed in steel tubes

1984 ◽  
Vol 42 ◽  
pp. 662-663
Author(s):  
Y. L. Chen ◽  
J. R. Bradley
Keyword(s):  
Stainless Steel ◽  
Carbon Steel ◽  
Catalyst Particle ◽  
Pyrolytic Carbon ◽  
Plain Carbon Steel ◽  
304 Stainless Steel ◽  
Hydrocarbon Gases ◽  
Steel Tubes ◽  
Filamentous Carbon ◽  
Carbon Filaments

Considerable effort has been directed toward an improved understanding of the production of the strong and stiff ∼ 1-20 μm diameter pyrolytic carbon fibers of the type reported by Koyama and, more recently, by Tibbetts. These macroscopic fibers are produced when pyrolytic carbon filaments (∼ 0.1 μm or less in diameter) are thickened by deposition of carbon during thermal decomposition of hydrocarbon gases. Each such precursor filament normally lengthens in association with an attached catalyst particle. The subject of filamentous carbon formation and much of the work on characterization of the catalyst particles have been reviewed thoroughly by Baker and Harris. However, identification of the catalyst particles remains a problem of continuing interest. The purpose of this work was to characterize the microstructure of the pyrolytic carbon filaments and the catalyst particles formed inside stainless steel and plain carbon steel tubes. For the present study, natural gas (∼; 97 % methane) was passed through type 304 stainless steel and SAE 1020 plain carbon steel tubes at 1240°K.

Model, simulation and experiments for a Buoyancy Organic Rankine Cycle

2020 ◽  
Vol 92 (1) ◽  
pp. 10906
Author(s):  
Jeroen Schoenmaker ◽  
Pâmella Gonçalves Martins ◽  
Guilherme Corsi Miranda da Silva ◽  
Julio Carlos Teixeira
Keyword(s):  
Model Simulation ◽  
Organic Rankine Cycle ◽  
Thermodynamic Cycle ◽  
Rankine Cycle ◽  
Test Body ◽  
Working Fluid ◽  
Proof Of Concept ◽  
Energy Scenario ◽  
New Type ◽  
Fluid Reservoir

Organic Rankine Cycle (ORC) systems are increasingly gaining relevance in the renewable and sustainable energy scenario. Recently our research group published a manuscript identifying a new type of thermodynamic cycle entitled Buoyancy Organic Rankine Cycle (BORC) [J. Schoenmaker, J.F.Q. Rey, K.R. Pirota, Renew. Energy 36, 999 (2011)]. In this work we present two main contributions. First, we propose a refined thermodynamic model for BORC systems accounting for the specific heat of the working fluid. Considering the refined model, the efficiencies for Pentane and Dichloromethane at temperatures up to 100 °C were estimated to be 17.2%. Second, we show a proof of concept BORC system using a 3 m tall, 0.062 m diameter polycarbonate tube as a column-fluid reservoir. We used water as a column fluid. The thermal stability and uniformity throughout the tube has been carefully simulated and verified experimentally. After the thermal parameters of the water column have been fully characterized, we developed a test body to allow an adequate assessment of the BORC-system's efficiency. We obtained 0.84% efficiency for 43.8 °C working temperature. This corresponds to 35% of the Carnot efficiency calculated for the same temperature difference. Limitations of the model and the apparatus are put into perspective, pointing directions for further developments of BORC systems.

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